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公开(公告)号：US12214894B1
公开(公告)日：2025-02-04
申请号：US18667065
申请日：2024-05-17
Applicant: Archer Aviation Inc.
Inventor： Scott Graves
IPC: F16H3/091 , B64C29/00 , B64D27/33 , B64D35/021
Abstract: A motor gearbox assembly for an aircraft may comprise a layshaft configured to transmit torque from a rotor to a main power output shaft. The motor gearbox assembly may comprise a gearbox housing, a stator mounted inside the gearbox housing, a rotor rotatably mounted inside the stator on a main power output shaft and a layshaft rotatably mounted in the gearbox housing outside of the stator. The motor gearbox assembly may comprise a first ear reduction between the rotor and the layshaft, and a second gear reduction between the layshaft and the main power output shaft.
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公开(公告)号：US12129040B2
公开(公告)日：2024-10-29
申请号：US18620479
申请日：2024-03-28
Applicant: Archer Aviation Inc.
Inventor： Scott Graves , Alan D. Tepe
CPC classification number: B64D27/24 , B64C29/0033 , B64D33/08
Abstract: An electric propulsion system for a vertical take-off and landing (VTOL) aircraft having a heat exchanger to cool fluids used in an electrical engine, the electric propulsion system comprising at least one electrical engine mechanically connected directly or indirectly to a fuselage of the VTOL aircraft and electrically connected to an electrical power source. The electrical engine may comprise an electrical motor having a stator and a rotor; a gearbox assembly comprising a sun gear; at least one planetary gear; a ring gear; and a planetary carrier. The electric engine may include an inverter assembly comprising a thermal plate and an inverter assembly housing; an end bell assembly that is connected to the thermal plate of the inverter assembly; and a heat exchanger comprising an array of cooling fins and tubes.
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公开(公告)号：US11958621B1
公开(公告)日：2024-04-16
申请号：US18531357
申请日：2023-12-06
Applicant: Archer Aviation Inc.
Inventor： Scott Graves
IPC: B64D27/24 , B64C11/30 , B64C27/12 , B64C27/54 , B64C29/00 , B64D33/08 , B64D35/02 , H02K5/20 , H02K7/08 , H02K7/116 , H02K9/19 , H02K11/33 , H02K7/00
CPC classification number: B64D27/24 , B64C27/54 , B64C29/0008 , B64C29/0033 , B64D33/08 , B64D35/02 , H02K5/203 , H02K7/08 , H02K7/116 , H02K9/19 , H02K11/33 , H02K7/006
Abstract: An electric propulsion system for a vertical take-off and landing (VTOL) aircraft, the electric propulsion system including an electrical motor having a stator and a rotor. The electric propulsion system may include a main shaft possessing at least one shoulder on an outer surface of the main shaft. The electric propulsion system may include a gearbox assembly comprising a sun gear that is concentrically aligned with the main shaft at least one planetary gear that interfaces with the sun gear. The electric propulsion system may include a planetary carrier, wherein a center of the planetary carrier is concentrically aligned with the main shaft. The electric propulsion system may include a propeller flange assembly that travels through the rotor, and an axial buttress positioned in the at least one shoulder located on the main shaft.
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公开(公告)号：US12234021B2
公开(公告)日：2025-02-25
申请号：US18391266
申请日：2023-12-20
Applicant: Archer Aviation Inc.
Inventor： Scott Graves
IPC: B64D27/24 , B64C27/54 , B64C29/00 , B64D33/08 , B64D35/02 , H02K1/27 , H02K1/32 , H02K5/20 , H02K7/08 , H02K7/116 , H02K9/19 , H02K11/33 , H02K15/03 , H02K7/00
Abstract: The present disclosure relates generally to a method for balancing a rotor of an electrical engine of an electrical propulsion system comprising: identifying an axis of rotation of a rotor, wherein the rotor comprises a sacrificial layer having a mass M formed along a circumference of the rotor; determining an imbalance present in the rotor by rotating the rotor about the axis of rotation, wherein determining an imbalance includes marking the rotor, rotating the rotor, and detecting an amplitude of the imbalance; calculating an amount of mass k to add or remove at a position p along the sacrificial layer such that a center of mass of the rotor coincides with the axis of rotation of the rotor; and removing an amount of mass r from the sacrificial layer such that an amount of remainder mass n is present along the circumference of the rotor.
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公开(公告)号：US11975853B2
公开(公告)日：2024-05-07
申请号：US18302285
申请日：2023-04-18
Applicant: Archer Aviation Inc.
Inventor： Scott Graves , Alan D. Tepe
CPC classification number: B64D27/24 , B64C29/0033 , B64D33/08
Abstract: An electric propulsion system for a vertical take-off and landing (VTOL) aircraft having a heat exchanger to cool fluids used in an electrical engine, the electric propulsion system comprising at least one electrical engine mechanically connected directly or indirectly to a fuselage of the VTOL aircraft and electrically connected to an electrical power source. The electrical engine may comprise an electrical motor having a stator and a rotor; a gearbox assembly comprising a sun gear; at least one planetary gear; a ring gear; and a planetary carrier. The electric engine may include an inverter assembly comprising a thermal plate and an inverter assembly housing; an end bell assembly that is connected to the thermal plate of the inverter assembly; and a heat exchanger comprising an array of cooling fins and tubes.
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Patent Agency Ranking
公开(公告)号：US11787551B1
公开(公告)日：2023-10-17
申请号：US18147452
申请日：2022-12-28
Applicant: Archer Aviation, Inc.
Inventor： Scott Graves , Alan D. Tepe , Robert Wayne Moore
CPC classification number: B64D27/24 , B64C29/0008 , B64D33/08 , H02K5/203 , H02K7/08 , H02K7/116 , H02K9/19 , H02K11/33
Abstract: An electric propulsion system for a vertical takeoff-and-landing aircraft having an inverter assembly, a gearbox assembly, an electric motor assembly. The inverter assembly, the gearbox assembly, and the electric motor assembly may be substantially aligned along an axis. The inverter assembly, a gearbox assembly, and electric motor assembly may each abut at least one of the others. The electric engine may use a liquid, such as oil, for cooling and lubricating components of the inverter assembly, gearbox assembly, and electric motor assembly. Further, the electric engine may use volumes of oil for cooling and lubricating components below a threshold volume so that the electric engines do not require a fire protective barrier.
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公开(公告)号：US12227300B2
公开(公告)日：2025-02-18
申请号：US18620917
申请日：2024-03-28
Applicant: Archer Aviation Inc.
Inventor： Scott Graves , Robert Wayne Moore
IPC: H02K11/33 , B60L15/06 , B60L15/38 , B64C27/54 , B64C29/00 , B64D27/24 , B64D33/08 , B64D35/02 , F16B2/06 , F16H57/08 , H02K1/27 , H02K1/32 , H02K5/124 , H02K5/20 , H02K7/08 , H02K7/116 , H02K9/19 , H02K15/03 , H02M7/5395 , H02P21/00 , H02P25/16 , H02P27/06 , H02P27/08 , H02K7/00
Abstract: An electric propulsion system comprising an electric motor assembly. The electric motor assembly may include a housing having an internal volume, a stator ring disposed about a perimeter of the internal volume, and a rotor positioned within the stator. The electric motor assembly may include a main shaft connected to the rotor via a gear reduction, wherein the main shaft extends through the rotor. The electric motor assembly may include a collar connected to the main shaft, wherein the collar encircles the main shaft, and at least a portion of the collar is configured to direct a fluid away from the main shaft and toward the stator ring.
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公开(公告)号：US12208908B2
公开(公告)日：2025-01-28
申请号：US18620493
申请日：2024-03-28
Applicant: Archer Aviation Inc.
Inventor： Scott Graves , Alan D. Tepe
IPC: B64C29/00 , B60L15/06 , B60L15/38 , B64C27/54 , B64D27/24 , B64D27/30 , B64D33/08 , B64D35/02 , F16B2/06 , F16H57/08 , H02K1/27 , H02K1/32 , H02K5/124 , H02K5/20 , H02K7/08 , H02K7/116 , H02K9/19 , H02K11/33 , H02K15/03 , H02M7/5395 , H02P21/00 , H02P25/16 , H02P27/06 , H02P27/08 , H02K7/00
Abstract: An electric propulsion system for a vertical take-off and landing (VTOL) aircraft having a heat exchanger to cool fluids used in an electrical engine, the electric propulsion system comprising at least one electrical engine mechanically connected directly or indirectly to a fuselage of the VTOL aircraft and electrically connected to an electrical power source. The electrical engine may comprise an electrical motor having a stator and a rotor; a gearbox assembly comprising a sun gear; at least one planetary gear; a ring gear; and a planetary carrier. The electric engine may include an inverter assembly comprising a thermal plate and an inverter assembly housing; an end bell assembly that is connected to the thermal plate of the inverter assembly; and a heat exchanger comprising an array of cooling fins and tubes.
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公开(公告)号：US12122527B2
公开(公告)日：2024-10-22
申请号：US18622647
申请日：2024-03-29
Applicant: Archer Aviation Inc.
Inventor： Scott Graves , Alan Baldwin , Stephen Michael Spiteri , Wei Wu , Alan D. Tepe
CPC classification number: B64D27/24 , B64C29/0033 , H02P25/16 , H02P27/06
Abstract: An electrical propulsion system for a vertical take-off and landing (VTOL) aircraft comprises an electrical motor assembly and an inverter assembly. The inverter assembly comprises a housing, a capacitor assembly, at least one printed circuit board assembly (PCBA), and a plurality of positioning pins. The capacitor assembly comprises a center hole, at least one capacitor, a capacitor housing having at least one busbar, and a plurality of through holes in the capacitor housing. The capacitor assembly and the at least one PCBA are positioned inside the housing. The plurality of positioning pins pass through the through the plurality of through holes of the capacitor housing and the at least one PCBA and are connected to the housing.
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公开(公告)号：US12024304B2
公开(公告)日：2024-07-02
申请号：US18299276
申请日：2023-04-12
Applicant: Archer Aviation Inc.
Inventor： Scott Graves , Robert Wayne Moore
IPC: H02K11/33 , B60L15/06 , B60L15/38 , B64C27/54 , B64C29/00 , B64D27/24 , B64D33/08 , B64D35/02 , F16B2/06 , F16H57/08 , H02K1/27 , H02K1/32 , H02K5/124 , H02K5/20 , H02K7/08 , H02K7/116 , H02K9/19 , H02K15/03 , H02M7/5395 , H02P21/00 , H02P25/16 , H02P27/06 , H02P27/08 , H02K7/00
CPC classification number: B64D27/24 , B60L15/06 , B60L15/38 , B64C27/54 , B64C29/0008 , B64C29/0033 , B64D33/08 , B64D35/02 , F16B2/06 , F16H57/08 , H02K1/27 , H02K1/32 , H02K5/124 , H02K5/203 , H02K7/08 , H02K7/116 , H02K9/19 , H02K11/33 , H02K15/03 , H02M7/5395 , H02P21/50 , H02P25/16 , H02P27/06 , H02P27/08 , B60L2200/10 , B60L2210/40 , H02K7/006
Abstract: An electric propulsion system comprising an electric motor assembly. The electric motor assembly may include a housing having an internal volume, a stator ring disposed about a perimeter of the internal volume, and a rotor positioned within the stator. The electric motor assembly may include a main shaft connected to the rotor via a gear reduction, wherein the main shaft extends through the rotor. The electric motor assembly may include a collar connected to the main shaft, wherein the collar encircles the main shaft, and at least a portion of the collar is configured to direct a fluid away from the main shaft and toward the stator ring.
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